A guidance and control study for a long-range air-to-air missile

Date

2024-9-03

Author

Karabağ, Burak Can

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In the guidance and control area, the pursuit of a highly maneuverable evasive airborne target by an air-to-air missile through a long range is a challenging problem. For the air-to-air missiles, precision is an important requirement. The impact time and velocity should also be taken into consideration in the case of long ranges. In this thesis, a hybrid guidance law consisting of an optimal midcourse phase and a terminal phase with standard Proportional Navigation Guidance (PNG) is proposed for a beyond-visual-range air-to-air missile. The midcourse phase of the proposed guidance law is posed and solved as an optimal control problem. In the optimal midcourse phase, the impact time is minimized through nonlinear programming via the direct collocation method. The transition from the midcourse to the terminal phase is described as entering a sphere around the target, which has an appropriately predetermined radius for an effective terminal phase. Optimization of the midcourse phase also considers the terminal phase. It provides an optimal entrance point to the mentioned sphere with an optimal Line-of-Sight (LOS) angle. Entering through this point as such means minimizing maneuvers and acceleration demands of the missile. Moreover, the proposed guidance law considers the limits of the physical parameters such as angle of attack and fin deflections as well and keeps them within the limits by formulating them as path constraints in the problem. The performance of the proposed guidance law is assessed by means of several simulations of different interception scenarios.

Subject Keywords

Beyond visual range air-to-air missile, Ramjet propulsion, Optimal midcourse guidance, Nonlinear programming, Path constraints

URI

https://hdl.handle.net/11511/111310

Collections

Graduate School of Natural and Applied Sciences, Thesis